58762 Federal Register / Vol. 77, No. 185 / Monday, September 24, 2012 / Rules and Regulations 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–19–06 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER): 

Amendment 39–17201. Docket No. 

FAA–2012–0638; Directorate Identifier 

2011–NM–266–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 29, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Empresa Brasileira de 

Aeronautica S.A. (EMBRAER) Model EMB– 

145, –145ER, –145MR, –145LR, –145MP, and 

–145EP airplanes; and Model EMB–135BJ, 

–135ER, –135KE, –135KL, and –135LR 

airplanes; certificated in any category; all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Reason 

This AD was prompted by a report of a 

lightning strike hitting an airplane tail boom 

causing certain rear bulkhead parts to jam an 

elevator control rod. We are issuing this AD 

to prevent lightning strikes from causing 

certain parts to contact the airplane pitch 

control system, which could reduce airplane 

controllability. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

Within 5,000 flight hours or 48 months 

after the effective date of this AD, whichever 

occurs first: Install or rework, as applicable, 

metallic diverters and aluminum sheets; 

modify the light assembly on the tail boom 

rear movable fairing; and replace the hood 

assembly with a new hood assembly having 

part number (P/N) 145–23046–403 and 

reroute its electrical harness. Do all the 

actions in accordance with the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145LEG–55–0013, dated 

September 8, 2011 (for Model EMB–135BJ 

airplanes); or EMBRAER Service Bulletin 

145–55–0030, Revision 05, dated July 29, 

2011 (for Model EMB–145 and EMB–135, 

except –135BJ, airplanes). 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1175; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to MCAI Brazilian Airworthiness 

Directive 2011–11–01, dated November 30, 

2011, and the following service information, 

for related information. 

(1) EMBRAER Service Bulletin 145LEG– 

55–0013, dated September 8, 2011. 

(2) EMBRAER Service Bulletin 145–55– 

0030, Revision 05, dated July 29, 2011. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) EMBRAER Service Bulletin 145LEG–55– 

0013, dated September 8, 2011. 

(ii) EMBRAER Service Bulletin 145–55– 

0030, Revision 05, dated July 29, 2011. 

(3) For service information identified in 

this AD, contact Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone 

+55 12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email 

distrib@embraer.com.br; Internet http:// 

www.flyembraer.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 6, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23277 Filed 9–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0821; Directorate 

Identifier 2010–NE–30–AD; Amendment 39– 

17183; AD 2012–18–07] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Rolls-Royce plc (RR) RB211-Trent 

875–17, RB211-Trent 877–17, RB211- 

Trent 884–17, RB211-Trent 884B–17, 

RB211-Trent 892–17, RB211-Trent 

892B–17, and RB211-Trent 895–17 

turbofan engines. That AD currently 

requires initial and repetitive ultrasonic 

inspections (UIs) of certain low-pressure 

(LP) compressor blades identified by 

serial number (S/N). This new AD 

requires the same actions but expands 

the population of blades. This AD was 

prompted by the need to add the 

inspections of the LP compressor blades 

listed by S/N in Appendices 3H through 

3L of RR plc Alert Service Bulletin 

(ASB) No. RB.211–72–AG244, Revision 

4, dated December 22, 2011. We are 

issuing this AD to prevent multiple LP 

compressor blades from failing due to 

blade root cracks, which could lead to 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD is effective October 29, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 


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Federal Register / Vol. 77, No. 185 / Monday, September 24, 2012 / Rules and Regulations 58763 

of a certain publication listed in the AD 

as of October 29, 2012. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE248BJ, 

phone: 011–44–1332–242424; fax: 011– 

44–1332–245418, or email: http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238– 

7199; email: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–06–23 (77 

FR 20508, April 5, 2012). That AD 

applies to the specified products. The 

NPRM published in the Federal 

Register on May 3, 2012 (77 FR 26216). 

That NPRM proposed to continue to 

require initial and repetitive UIs of 

certain LP compressor blades identified 

by S/N. This AD requires the same 

actions but expands the population of 

blades. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Modify Initial Inspection 

Thresholds 

Commenters RR and The Boeing 

Company (Boeing) requested that the 

initial inspection thresholds listed in 

Table 1 of the proposed AD be the same 

as those in RR ASB RB.211–72–AG244. 

Alternatively, RR and Boeing asked that 

we adjust the calendar months after the 

effective date of the AD to make them 

equivalent to the calendar dates in the 

ASB. RR claims that allowing parts to 

remain on wing longer than the times 

specified in the ASB will increase the 

risk of a fan blade failure before a crack 

is detected. 

We do not agree. The number of 

months for compliance after the 

effective date of this AD is the same as 

in the EASA AD 2012–0025, dated 

February 8, 2012. Also, shortening the 

initial inspection thresholds now would 

require renotice and therefore delay 

implementation of the AD. We did not 

change the AD. 

Request To Revise Unsafe Condition 

Statement 

RR asked that we change the unsafe 

condition statement in the AD to 

indicate that the AD is being issued to 

prevent multiple blades from the same 

engine from failing. RR indicated that 

this change is needed because a single 

blade failure from the root is, by design, 

a contained event. 

We agree because multiple blades in 

an engine may develop cracks and fail 

if not inspected. We changed the AD by 

revising the unsafe condition statement 

in paragraph (d) of the AD from: ‘‘We 

are issuing this AD to prevent LP 

compressor blades from failing due to 

blade root cracks, which could lead to 

uncontained engine failure and damage 

to the airplane’’ to ‘‘We are issuing this 

AD to prevent multiple LP compressor 

blades from failing due to blade root 

cracks, which could lead to uncontained 

engine failure and damage to the 

airplane.’’ 

Request To Revise Compliance 

Paragraph (e)(3) 

Commenter American Airlines 

(American) requested that we change 

paragraph (e)(3) from ‘‘* * * and 

paragraphs 1. through 3.B. of Appendix 

1 of that ASB, or paragraphs 3.B.(1) 

through 3.B.(3) of Accomplishment 

Instructions of RR ASB No. RB.211–72– 

AG244 * * *,’’ to ‘‘* * * and 

paragraphs 1. through 3.B. of Appendix 

1 of that ASB, or paragraph 3.B.(3) of 

Accomplishment Instructions of RR 

ASB No. RB.211–72–AG244 * * *.’’. 

American argued that paragraphs 3.B.(1) 

and 3.B.(2), which require removal of 

the air intake fairing/spinner and 

spinner extension and annulus fillers, 

are not needed to resolve the unsafe 

condition noted in the AD. 

We agree in part. We agree to remove 

the references to paragraphs 3.B.(1) and 

3.B.(2) from the AD because it is not 

necessary to mandate the procedures 

used to remove the air intake fairing/ 

spinner and spinner extension and 

annulus fillers. We disagree that 

removal of these parts does not need to 

be mentioned in the AD because these 

parts need to be removed before 

performing the UI. We therefore revised 

paragraph (e)(3) in the AD from: ‘‘Use 

paragraph 3.A.(2) of Accomplishment 

Instructions of RR ASB No. RB.211–72– 

AG244, Revision 4, dated December 22, 

2011, and paragraphs 1. through 3.B. of 

Appendix 1 of that ASB, or paragraphs 

3.B.(1) through 3.B.(3) of 

Accomplishment Instructions of RR 

ASB No. RB.211–72–AG244, Revision 4, 

dated December 22, 2011, and 

paragraphs 1. through 3.C. of Appendix 

2 of that ASB, to perform the UIs.’’ to 

‘‘Use paragraph 3.A.(2) of 

Accomplishment Instructions of RR 

ASB No. RB.211–72–AG244, Revision 4, 

dated December 22, 2011, and 

paragraphs 1. through 3.B. of Appendix 

1 of that ASB, or paragraphs 3.B.(3) of 

Accomplishment Instructions of RR 

ASB No. RB.211–72–AG244, Revision 4, 

dated December 22, 2011, and 

paragraphs 1. through 3.C. of Appendix 

2 of that ASB, to perform the UIs. Prior 

to inspecting the blades per paragraph 

3.B.(3) of the Accomplishment 

Instructions remove the air intake 

fairing/spinner and spinner extension 

and annulus fillers.’’ 

Request To Revise Compliance 

Paragraph (e)(6) 

American requested that paragraph 

(e)(6) of the AD be revised to read: 

‘‘After the effective date of this AD, do 

not install any affected LP compressor 

blade that has reached the initial 

inspection threshold in Table 1, unless 

it has passed the UI required by this 

AD.’’ American indicated that the 

wording of the proposed AD implied 

that if a blade fails a visual inspection, 

it may not be reinstalled even if it 

passes a subsequent UI. 

We agree. We revised the paragraph to 

read: ‘‘After the effective date of this 

AD, do not install any affected LP 

compressor blade that has reached the 

initial inspection threshold in Table 1 to 

paragraph (e), unless it has passed the 

UI required by this AD.’’ We also moved 

this paragraph to a separate Installation 

Prohibition paragraph (f). 

Request To Revise Previous Credit 

Paragraph 

American asked that the AD allow 

compressor blades inspected 

ultrasonically before the effective date 


emcdonald on DSK67QTVN1PROD with RULES
58764 Federal Register / Vol. 77, No. 185 / Monday, September 24, 2012 / Rules and Regulations 

of this AD using RR SB RB.211–72– 

E175, Revision 7, dated April 11, 2011, 

to be installed without further 

inspection. American indicated that the 

UI instructions in SB RB.211–E175, 

Revision 7, are identical to the UI 

instructions in ASB RB.211–72–AG244. 

We agree. We changed the Credit for 

Previous Actions paragraph in the AD 

from, ‘‘You may take credit for the 

initial inspection that is required by 

paragraph (e)(1) of this AD if you 

performed the initial inspection before 

the effective date of this AD using RR 

ASB No. RB.211–72–AG244, dated 

August 7, 2009; ASB No. RB.211–72– 

AG244, Revision 1, dated January 26, 

2010; ASB No. RB.211–72–AG244, 

Revision 2, dated August 18, 2011; or 

ASB No. RB.211–72–AG244, Revision 3, 

dated December 13, 2011,’’ to ‘‘You may 

take credit for the initial inspection that 

is required by paragraph (e)(1) of this 

AD if you performed the initial 

inspection before the effective date of 

this AD using RR ASB No. RB.211–72– 

AG244, dated August 7, 2009; ASB No. 

RB.211–72–AG244, Revision 1, dated 

January 26, 2010; ASB No. RB.211–72– 

AG244, Revision 2, dated August 18, 

2011, ASB No. RB.211–72–AG244, 

Revision 3, dated December 13, 2011 or 

RB.211–72–E175, Revision 7, dated 

April 11, 2011.’’ 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects about 158 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 3 hours per engine inspection 

and six inspections will be needed per 

year. The average labor rate is $85 per 

work-hour. We estimate that one LP 

compressor blade per year will need 

replacement at a cost of about $82,000. 

Based on these figures, we estimate the 

annual cost of the AD on U.S. operators 

to be $323,740. Our cost estimate is 

exclusive of possible warranty coverage. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2012–06–23, Amendment 39–17004 (77 

FR 20508, April 5, 2012), and adding 

the following new AD: 

2012–18–07 Rolls-Royce plc: Amendment 

39–17183; Docket No. FAA–2010–0821; 

Directorate Identifier 2010–NE–30–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 29, 2012. 

(b) Affected ADs 

This AD supersedes AD 2012–06–23 (77 

FR 20508, April 5, 2012). 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211-Trent 875–17, RB211-Trent 877–17, 

RB211-Trent 884–17, RB211-Trent 884B–17, 

RB211-Trent 892–17, RB211-Trent 892B–17, 

and RB211-Trent 895–17 turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by the need to add 

the inspections of the low-pressure (LP) 

compressor blades listed by serial number (S/ 

N) in Appendices 3H through 3L of RollsRoyce plc Alert Service Bulletin (ASB) No. 

RB.211–72–AG244, Revision 4, dated 

December 22, 2011. We are issuing this AD 

to prevent multiple LP compressor blades 

from failing due to blade root cracks, which 

could lead to uncontained engine failure and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Perform an initial ultrasonic inspection 

(UI) of the affected LP compressor blades 

identified by S/N in Appendices 3A through 

3L of RR ASB No. RB.211–72–AG244, 

Revision 4, dated December 22, 2011. Use 

Table 1 to paragraph (e) of this AD to 

determine your initial inspection threshold. 

TABLE 1 TO PARAGRAPH (e)—INITIAL INSPECTION THRESHOLDS

Appendix number of RR ASB Number RB.211–72–AG244, Revision 4, 

that identifies affected LP compressor blades by S/N Initial inspection threshold 

3A and 3B .............................................................................................................. Within 70 flight cycles after the effective date of this AD. 

3C ........................................................................................................................... Within 10 months after the effective date of this AD. 

3D ........................................................................................................................... Within 22 months after the effective date of this AD. 

3E ........................................................................................................................... Within 34 months after the effective date of this AD. 

3F ........................................................................................................................... Within 46 months after the effective date of this AD. 


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TABLE 1 TO PARAGRAPH (e)—INITIAL INSPECTION THRESHOLDS—Continued 

Appendix number of RR ASB Number RB.211–72–AG244, Revision 4, 

that identifies affected LP compressor blades by S/N Initial inspection threshold 

3G .......................................................................................................................... Within 58 months after the effective date of this AD. 

3H ........................................................................................................................... Within 70 months after the effective date of this AD. 

3I ............................................................................................................................ Within 82 months after the effective date of this AD. 

3J ........................................................................................................................... Within 94 months after the effective date of this AD. 

3K ........................................................................................................................... Within 106 months after the effective date of this AD. 

3L ........................................................................................................................... Within 118 months after the effective date of this AD. 

(2) Thereafter, perform repetitive UIs of the 

affected LP compressor blades within every 

100 flight cycles. 

(3) Use paragraph 3.A.(2) of 

Accomplishment Instructions of RR ASB No. 

RB.211–72–AG244, Revision 4, dated 

December 22, 2011, and paragraphs 1. 

through 3.B. of Appendix 1 of that ASB, or 

paragraphs 3.B.(3) of Accomplishment 

Instructions of RR ASB No. RB.211–72– 

AG244, Revision 4, dated December 22, 2011, 

and paragraphs 1. through 3.C. of Appendix 

2 of that ASB, to perform the UIs. Prior to 

inspecting the blades per paragraph 3.B.(3) of 

the Accomplishment Instructions remove the 

air intake fairing/spinner and spinner 

extension and annulus fillers. 

(4) Do not return to service any engine with 

blades that failed the inspection required by 

this AD. 

(5) For blades that are removed from the 

engine and pass inspection, re-apply dry film 

lubricant before re-installing the blades. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any affected LP compressor blade that 

has reached the initial inspection threshold 

in Table 1 to paragraph (e) of this AD, unless 

it has passed the UI required by this AD. 

(g) Credit for Previous Actions 

You may take credit for the initial 

inspection that is required by paragraph 

(e)(1) of this AD if you performed the initial 

inspection before the effective date of this AD 

using RR ASB No. RB.211–72–AG244, dated 

August 7, 2009; RR ASB No. RB.211–72– 

AG244, Revision 1, dated January 26, 2010; 

RR ASB No. RB.211–72–AG244, Revision 2, 

dated August 18, 2011; RR ASB No. RB.211– 

72–AG244, Revision 3, dated December 13, 

2011; or RR RB.211–72–E175, Revision 7, 

dated April 11, 2011. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238–7199; 

email: alan.strom@faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0025, dated February 8, 

2012, for related information. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Rolls-Royce plc Alert Service Bulletin 

No. RB.211–72–AG244, Revision 4, including 

appendices 1, 2, and 3A through 3L, dated 

December 22, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ, phone: 011–44–1332– 

242424; fax: 011–44–1332–245418; email: 

http://www.rolls-royce.com/contact/ 

civil_team.jsp. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

August 29, 2012. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–23442 Filed 9–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0593; Directorate 

Identifier 2011–NM–238–AD; Amendment 

39–17200; AD 2012–19–05] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by reports of burned contacts 

in a certain production break plug and 

its corresponding receptacle. This AD 

requires modifying galley power supply 

wiring by disconnecting it from the 

affected plug/receptacle and 

reconnecting the power supply wiring 

through splices. We are issuing this AD 

to prevent a high electrical load, which 

might lead to overheating of the galley 

power supply wiring and/or the 

electrical connector and consequent 

smoke or fire in the galley area, which 

could result in damage to the airplane 

and injury to occupants. 

DATES: This AD becomes effective 

October 29, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 29, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1137; 

fax (425) 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 12, 2012 (77 FR 34872). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Reports have been received about burned 

contacts in production break plug P 4259B 

and corresponding receptacle J 4259A. After 

investigation, it was concluded that the high 


emcdonald on DSK67QTVN1PROD with RULES